Assembly for sealing an annular gap between an inner structure and an outer structure

Abstract

A system is provided for a nacelle of an aircraft propulsion system. This system includes a tubular outer structure, a tubular inner structure and a seal assembly. The tubular inner structure projects through a bore of the tubular outer structure. The seal assembly is configured to close an end of an annulus between the tubular outer structure and the tubular inner structure. The seal assembly includes a seal land and a seal element. The seal land includes a seal land mount that circumscribes and is attached to the tubular inner structure. The seal land mount is configured with a v-shaped sectional geometry. The seal element is attached to the tubular outer structure. The seal element circumscribes and is sealingly engaged with the seal land. The seal element may be configured from or otherwise includes a polymer material.

What is claimed is: 
     
       1. A system for a nacelle of an aircraft propulsion system, comprising:
 a tubular outer structure; 
 a tubular inner structure projecting through a bore of the tubular outer structure; and 
 a seal assembly configured to close an end of an annulus between the tubular outer structure and the tubular inner structure, the seal assembly including a seal land and a seal element; 
 the seal land comprising a seal land mount that circumscribes and is attached to the tubular inner structure, the seal land mount configured with a v-shaped sectional geometry, and the seal land further including an annular array of cooling elements; and 
 the seal element attached to the tubular outer structure, the seal element circumscribing and sealingly engaged with the seal land, and the seal element comprising a polymer material. 
 
     
     
       2. A system for a nacelle of an aircraft propulsion system, comprising:
 a tubular outer structure; 
 an anti-icing system for an inlet structure of the nacelle, the anti-icing system comprising a tubular inner structure that projects through a bore of the tubular outer structure; and 
 a seal assembly configured to close an end of an annulus between the tubular outer structure and the tubular inner structure, the seal assembly including a seal land and a seal element; 
 the seal land comprising a seal land mount that circumscribes and is attached to the tubular inner structure, the seal land mount configured with a v-shaped sectional geometry; and 
 the seal element attached to the tubular outer structure, the seal element circumscribing and sealingly engaged with the seal land, and the seal element comprising a polymer material. 
 
     
     
       3. A system for a nacelle of an aircraft propulsion system, comprising:
 a tubular outer structure; 
 a tubular inner structure projecting through a bore of the tubular outer structure; and 
 a seal assembly configured to close an end of an annulus between the tubular outer structure and the tubular inner structure, the seal assembly including a seal land and a seal element; 
 the seal land comprising a seal land mount that circumscribes and is attached to the tubular inner structure, the seal land mount configured with a v-shaped sectional geometry, the seal land mount including an inner conical element and an outer conical element, an inner end of the inner conical element attached to the tubular inner structure, and an outer end of the inner conical element connected to an inner end of the outer conical element; and 
 the seal element attached to the tubular outer structure, the seal element circumscribing and sealingly engaged with the seal land, and the seal element comprising a polymer material. 
 
     
     
       4. The system of  claim 3 , wherein the seal land mount is configured with the v-shaped sectional geometry in a plane that is parallel with a centerline of the tubular inner structure. 
     
     
       5. The system of  claim 3 , wherein
 the seal land further includes a seal land tube; 
 the seal land mount extends along a path from the tubular inner structure to the seal land tube, and a length of the path is at least four times greater than a shortest distance from the tubular inner structure to the seal land tube; and 
 the seal element circumscribes and is sealingly engaged with the seal land tube. 
 
     
     
       6. The system of  claim 3 , wherein
 the seal land is configured to provide a restrictive heat conduction path from the tubular inner structure to an outer surface of the seal land; and 
 the seal element circumscribes and contacts the outer surface of the seal land. 
 
     
     
       7. The system of  claim 3 , wherein
 the seal land further includes a seal land tube; 
 an outer end of the outer conical element is connected to and radially within the seal land tube; and 
 the seal element circumscribes and contacts the seal land tube. 
 
     
     
       8. The system of  claim 7 , wherein
 the seal land further includes a second seal land mount; 
 the second seal land mount includes a second inner conical element and a second outer conical element; 
 an inner end of the second inner conical element is attached to the tubular inner structure; 
 an outer end of the second inner conical element is connected to an inner end of the second outer conical element; and 
 an outer end of the second outer conical element is connected to and radially within the seal land tube. 
 
     
     
       9. The system of  claim 3 , wherein
 the seal land further includes a seal land tube; 
 the seal land mount connects the seal land tube to the tubular inner structure; and 
 the seal element circumscribes and contacts the seal land tube. 
 
     
     
       10. The system of  claim 3 , wherein the seal element further includes fibrous material embedded within the polymer material. 
     
     
       11. The system of  claim 3 , wherein
 the seal assembly further comprises a second seal element attached to the tubular outer structure; 
 the second seal element circumscribes and is engaged with the seal land; and 
 the second seal element comprising a metal material. 
 
     
     
       12. The system of  claim 11 , wherein
 the seal land further includes a seal land tube; 
 the seal land mount connects the seal land tube to the tubular inner structure; and 
 the second seal element circumscribes and contacts the seal land tube. 
 
     
     
       13. The system of  claim 11 , wherein
 the seal land further includes a seal land tube and a plurality of cooling elements; 
 the seal land mount connects the seal land tube to the tubular inner structure; and 
 the cooling elements are arranged circumferentially about the seal land tube, and each of the cooling elements projects radially out from the seal land tube. 
 
     
     
       14. The system of  claim 13 , wherein
 the second seal element circumscribes the seal land tube; and 
 the second seal element axially contacts one or more of the cooling elements. 
 
     
     
       15. The system of  claim 11 , wherein the second seal element is configured as a turkey feather seal element. 
     
     
       16. The system of  claim 11 , wherein the seal element is clamped between the tubular outer structure and the second seal element. 
     
     
       17. A nacelle system for an aircraft propulsion system, comprising:
 an outer structure; 
 an inner structure located in an aperture of the outer structure; and 
 a seal assembly configured to seal a gap between the inner structure and the outer structure, the seal assembly including a seal land and a seal element; 
 the seal land including a seal land mount and a seal land tube connected to the inner structure by the seal land mount; 
 the seal land mount extending along a path from the inner structure to the seal land tube, wherein a length of the path is at least two times greater than a shortest distance from the inner structure to the seal land tube; and 
 the seal element attached to the outer structure, the seal element circumscribing and sealingly engaged with the seal land tube, and the seal element comprising a polymer material. 
 
     
     
       18. The nacelle system of  claim 17 , wherein
 the outer structure comprises a tubular outer structure; 
 the seal assembly further includes a second seal element; 
 the second seal element is attached to the outer structure; 
 the seal element circumscribes and is sealingly engaged with the seal land; and 
 the seal element comprises a metal material. 
 
     
     
       19. The nacelle system of  claim 17 , wherein
 the outer structure comprises a bulkhead; 
 the seal assembly further includes a second seal element; 
 the second seal element is attached to the outer structure; 
 the seal element circumscribes and is sealingly engaged with the seal land; and 
 the seal element comprises a metal material. 
 
     
     
       20. A nacelle system for an aircraft propulsion system, comprising:
 an outer structure; 
 an inner structure within an opening of the outer structure; and 
 a seal assembly configured to seal a gap between the inner structure and the outer structure, the seal assembly including a seal land, a polymer seal element and a non-polymer seal element; 
 the seal land circumscribing and mounted to the inner structure, and the seal land configured to provide a restrictive heat conduction path from the inner structure to an outer surface of the seal land; 
 the polymer seal element and the non-polymer seal element attached to the outer structure at a common location; 
 the polymer seal element circumscribing and sealingly engaged with the outer surface of the seal land; and 
 the non-polymer seal element circumscribing and sealingly engaged with the seal land.